GB1401018A - Flow control system - Google Patents

Flow control system

Info

Publication number
GB1401018A
GB1401018A GB3220574A GB3220574A GB1401018A GB 1401018 A GB1401018 A GB 1401018A GB 3220574 A GB3220574 A GB 3220574A GB 3220574 A GB3220574 A GB 3220574A GB 1401018 A GB1401018 A GB 1401018A
Authority
GB
United Kingdom
Prior art keywords
flow
section
engine
outlet
inlet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB3220574A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of GB1401018A publication Critical patent/GB1401018A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/80—Application in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1401018 Gas turbine ducted fan engines BOEING CO 30 Oct 1972 [8 Nov 1971 16 Feb 1972] 32205/74 Divided out of 1401017 Heading F1J [Also in Division F2] The invention relates to a flow control system comprising means for inverting the respective positions of two separate flow patterns between the inlet and outlet of the system, there being means for switching the flow patterns whereby the flow patterns may be non-inverted. The system is shown applied to a gas turbine ducted fan engine in Fig. 1, the flow of air A from the fan 26 and flow of air B from the intake 28 are inverted in passing through the flow control unit 20 so that the flow A which is radially inward of flow B at the inlet 22 is radially outward of flow B at the outlet 24. The flow A discharges through propulsion nozzle 30. The flow B passes to the compressor 32 of the gas turbine engine. Thus the engine acts as a ducted fan engine. The downstream portion 24 of the flow control unit may be rotated so that the unit does not cause flow inversion, the inner flow A from the fan 26 now passing to the inlet of the compressor, and the outer flow B now passing straight through from the intake 28 to the outlet 30, the engine thus acting as a straight-through gas turbine jet engine. A flow control unit is shown in Fig. 3 and the cross-sections taken at the planes 3a, 3b, 3c, 3d, 3e, 3f are shown in the corresponding Figs. A passage A at the inner radius at the inlet section 3a, becomes passage A at the outer radius at the outlet section 3f; the cross-sections of the passage A changes from an arcuate sector at section 3a, to a pentagonal section at 3b, to a triangular section with apex outward at 3c, to a trapezium section extending from the inner wall 62 to the outer wall 60 at 3d, to a triangular section with apex inward at 3e, to a pentagonal section, finally to an arcuate sector at 3f. The control unit is divided at the section 3d, the downstream portion 58 being angularly movable with respect to the upstream portion 56 whereby the flows may be inverted or not. The control member may alternatively be built-up from a series of duct portions as shown in Fig. 6 each of which has a rectangular opening 140 at the inlet end, the rectangle having the longer side of horizontal, the duct changing to a triangular section at 142 then to a rectangular section at the outlet 144, the rectangle having the longer side vertical. In Fig. 7, two such duct members 126, 126" are joined end-to-end and a similar pair of members 126''', 126"" are disposed to co-operate therewith. The downstream members 126''', 126"" are arranged to move laterally with respect to the upstream members 126', 126 " for control. The area of the duct at any point along its length is constant. Many applications of the invention are described.
GB3220574A 1971-11-08 1972-10-30 Flow control system Expired GB1401018A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US19642271A 1971-11-08 1971-11-08
US22685072A 1972-02-16 1972-02-16

Publications (1)

Publication Number Publication Date
GB1401018A true GB1401018A (en) 1975-07-16

Family

ID=26891896

Family Applications (2)

Application Number Title Priority Date Filing Date
GB3220574A Expired GB1401018A (en) 1971-11-08 1972-10-30 Flow control system
GB5000072A Expired GB1401017A (en) 1971-11-08 1972-10-30 Duct system

Family Applications After (1)

Application Number Title Priority Date Filing Date
GB5000072A Expired GB1401017A (en) 1971-11-08 1972-10-30 Duct system

Country Status (12)

Country Link
JP (1) JPS4861810A (en)
AU (1) AU463875B2 (en)
BE (1) BE791058A (en)
CA (1) CA963274A (en)
DE (1) DE2255085A1 (en)
DK (1) DK136668B (en)
FR (1) FR2172078B1 (en)
GB (2) GB1401018A (en)
IL (1) IL40739A (en)
IT (1) IT973440B (en)
NL (1) NL7215135A (en)
SE (1) SE385610B (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1389347A (en) * 1972-05-25 1975-04-03 Rolls Royce Gas turbine power plant
GB1415679A (en) * 1972-11-17 1975-11-26 Rolls Royce Gas turbine engine powerplant
US4142365A (en) * 1976-11-01 1979-03-06 General Electric Company Hybrid mixer for a high bypass ratio gas turbofan engine
FR2645911B1 (en) * 1989-04-18 1991-06-07 Snecma HIGH DILUTION MOTOR WITH UPSTREAM BLOWER AND DOWNSTREAM BLOWER
JPH04308326A (en) * 1991-04-03 1992-10-30 Mitsubishi Heavy Ind Ltd Flow path change-over device
GB2354041B (en) * 2000-07-04 2003-11-19 Adrian Alexander Hubbard Variable mode jet engine-compact
US8061980B2 (en) 2008-08-18 2011-11-22 United Technologies Corporation Separation-resistant inlet duct for mid-turbine frames
CN108252935A (en) * 2016-12-29 2018-07-06 上海鼓风机厂有限公司 Multistage culvert type axial flow compressor
CN114542286A (en) * 2022-03-04 2022-05-27 中国商用飞机有限责任公司 Engine model and airplane provided with same

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3527317A (en) * 1969-04-18 1970-09-08 Gen Electric Sound control of turbofan engines

Also Published As

Publication number Publication date
AU463875B2 (en) 1975-08-07
IT973440B (en) 1974-06-10
DK136668C (en) 1978-04-10
DK136668B (en) 1977-11-07
FR2172078B1 (en) 1976-10-29
DE2255085A1 (en) 1973-05-10
BE791058A (en) 1973-03-01
IL40739A0 (en) 1973-03-30
AU4860272A (en) 1974-05-09
SE385610B (en) 1976-07-12
CA963274A (en) 1975-02-25
FR2172078A1 (en) 1973-09-28
GB1401017A (en) 1975-07-16
IL40739A (en) 1975-03-13
JPS4861810A (en) 1973-08-29
NL7215135A (en) 1973-05-10

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee